CN106768791A - A kind of micro wind-tunnel balance - Google Patents
A kind of micro wind-tunnel balance Download PDFInfo
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- CN106768791A CN106768791A CN201611023820.8A CN201611023820A CN106768791A CN 106768791 A CN106768791 A CN 106768791A CN 201611023820 A CN201611023820 A CN 201611023820A CN 106768791 A CN106768791 A CN 106768791A
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- wind
- tunnel balance
- horizontal gird
- tunnel
- vertical beam
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention provides a kind of micro wind-tunnel balance, including：One variable cross-section profiled beam, a base, the variable cross-section profiled beam is L-type, it is divided into horizontal gird and vertical beam, there is model to install positioning end face and pointed projections for horizontal gird end, for installing fixed aerodynamic force test model, some notches are provided with horizontal gird and vertical beam as strain measurement region；The vertical beam bottom of the profiled beam is fixed on the base.The present invention devises a kind of micro wind-tunnel balance and test philosophy for the micro-force measurement of rarefied air wind tunnel environment.The balance body elastic element is made up of variable cross-section profiled beam, using high sensitivity strain testing technology, can measure the strain in some regions of flexible member；Aerodynamic drag, lift and the yaw forces of mN magnitudes, and the accordingly pitching moment of magnitude, yawing and rolling moment can be obtained by Inversion Calculation, altogether six components.
Description
Technical field
The present invention relates to a kind of air tunnel testing device, and in particular to a kind of micro wind-tunnel balance.
Background technology
Wind-tunnel balance is the important air tunnel testing device for measuring aircraft (model) aerodynamic force, but current wind-tunnel
Balance can not all measure simultaneously six components (aerodynamic drag of mN magnitudes, lift and yaw forces, and corresponding magnitude pitching power
Square, yawing and rolling moment) small power and torque.
So need badly it is a kind of can be while measuring six micro wind-tunnel balances of component.
The content of the invention
Six micro wind-tunnel balances of component can be simultaneously measured it is an object of the invention to provide a kind of.
In order to solve the above problems, the present invention provides a kind of micro wind-tunnel balance, including：
One variable cross-section profiled beam, a base, the variable cross-section profiled beam are L-type, be divided into horizontal gird and vertical beam is vertical
There is model to install positioning end face and pointed projections for beam, horizontal gird end, for installing fixed aerodynamic force test model, level
Some notches are provided with crossbeam and vertical beam as strain measurement region；The base is fixed in the vertical beam bottom of the profiled beam
On.
Further, the special-shaped beam section is cross, i.e., with orthogonal reinforcement.
Further, the wind-tunnel balance also has a briquetting, is fixed together with the base, for increasing stabilization
Property.
Further, the horizontal gird is located at Z axis negative sense, and vertical beam is located at Y-axis negative sense, and the two is mutually perpendicular to, reinforcement point
Wei Yu not be in XOY, XOZ, YOZ plane.
Further, the notch is 6, and 4 on horizontal gird, wherein 2 are located in XOZ planes, 2 flat positioned at YOZ
In face；2 in vertical beam, wherein 1 is located in XOY plane, 1 is located in YOZ planes.
Further, each measured zone sets 4 measuring points, that is, set 4 foil gauges and constitute a Wheatstone bridge, measurement
Around the bending strain of notch axial direction.
Relative to prior art, the present invention has following technique effect：
The present invention devises a kind of micro wind-tunnel balance and test is former for the micro-force measurement of rarefied air wind tunnel environment
Reason.The balance body elastic element is made up of variable cross-section profiled beam, using high sensitivity strain testing technology, can measure elasticity
The strain in some regions of element；Aerodynamic drag, lift and the yaw forces of mN magnitudes, and corresponding magnitude can be obtained by Inversion Calculation
Pitching moment, yawing and rolling moment, six components altogether.
Brief description of the drawings
Fig. 1 is the structural representation of the embodiment of the present invention.
Specific embodiment
Embodiments of the invention are described in detail below in conjunction with accompanying drawing.It should be noted that not conflicting
In the case of, the feature in embodiment and embodiment in the application can mutually be combined.
Embodiment one：
As shown in figure 1, the present invention provides a kind of micro wind-tunnel balance, including：One variable cross-section profiled beam, 1, base
2, variable cross-section profiled beam 1 is L-type, is divided into horizontal gird 11 and vertical beam 12, and there is the end of horizontal gird 11 model to install positioning end
Face 111 and pointed projections 112, for installing fixed aerodynamic force test model (not shown), horizontal gird 11 and vertical beam 12
On be provided with some notches 113 as strain measurement region；The bottom of vertical beam 12 of profiled beam is fixed on base 2.
Wind-tunnel balance also has a briquetting 3, is fixed together with base 2, for increasing stability.
Special-shaped beam section is cross, i.e., with orthogonal reinforcement.
Horizontal gird 11 is located at Z axis negative sense, and vertical beam 12 is located at Y-axis negative sense, and the two is mutually perpendicular to, and reinforcement is located at respectively
In XOY, XOZ, YOZ plane.
Notch 113 is 6, and 4 on horizontal gird 11, wherein 2 are located in XOZ planes, 2 are located in YOZ planes；It is vertical
2 on beam 12, wherein 1 is located in XOY plane, 1 is located in YOZ planes.
Each measured zone sets 4 measuring points, that is, set 4 foil gauges and constitute a Wheatstone bridge, measuring flume mouth region
The bending strain of domain axial direction.
Test philosophy
1) balance agent structure includes variable cross-section profiled beam, a base and a briquetting, as shown in Figure 1.To mark
Quasi- fastener connects briquetting and base, and profiled beam is clamped into corresponding position.Aerodynamic force test model is arranged on abnormity
Beam horizontal segment leading section, model is rigidly connected with special-shaped beam end；The aerodynamic force and aerodynamic moment that model bears will be transmitted, effect
Onto profiled beam.
2) profiled beam is used as the bullet for measuring aerodynamic drag, lift, yaw forces, pitching moment, yawing and rolling moment
Property element.It is made up of two pieces of orthogonal thin plates or shell in profiled beam main body, some notches is processed on beam as strain measurement region.
3) aerodynamic drag Fz, lift Fy, yaw forces Fx, pitching moment Mx, yawing My and rolling moment Mz's is common
Effect will cause profiled beam that complex bend occurs, and the bending strain of each region P1, P2, P3, P4, P5 and P6 is measured with foil gauge.
The Z-direction stretching/compressing strain that the sensing bending of four measuring points of each measured zone, wherein P1, P2, P3 and P4 is produced, P5 and P6
The Y-direction stretching/compressing strain that sensing bending is produced.
4) four foil gauges of each measured zone are constituted into a Wheatstone bridge, makes measured zone P1, P3 and P6 bridge pressures
Bending, P2 with P4 corresponding bending, P5 correspondence with Y-axis as rotary shaft of the output correspondence flexible member with X-axis as rotary shaft are with Z axis
It is the bending of rotary shaft, and the bridge pressure output cancel themselves that other deformations cause.So as to spring beam flexure theory from survey can be based on
Amount areal strain calculates pneumatic force component.
The preferred embodiments of the present invention are these are only, is not intended to limit the invention, for those skilled in the art
For member, the present invention can have various modifications and variations.All any modifications within the spirit and principles in the present invention, made,
Equivalent, improvement etc., should be included within the scope of the present invention.
Claims (6)
1. a kind of micro wind-tunnel balance, it is characterised in that including：
One variable cross-section profiled beam, a base, the variable cross-section profiled beam are L-type, are divided into horizontal gird and vertical beam, and level is horizontal
There is beam end model to install positioning end face and pointed projections, for installing fixed aerodynamic force test model, horizontal gird and vertical
Some notches are provided with beam as strain measurement region；The vertical beam bottom of the profiled beam is fixed on the base.
2. wind-tunnel balance as claimed in claim 1, it is characterised in that：
The special-shaped beam section is cross, i.e., with orthogonal reinforcement.
3. wind-tunnel balance as claimed in claim 2, it is characterised in that：
The wind-tunnel balance also has a briquetting, is fixed together with the base, for increasing stability.
4. wind-tunnel balance as claimed in claim 3, it is characterised in that：
The horizontal gird be located at Z axis negative sense, vertical beam be located at Y-axis negative sense, the two is mutually perpendicular to, reinforcement respectively be located at XOY,
In XOZ, YOZ plane.
5. wind-tunnel balance as claimed in claim 4, it is characterised in that：
The notch is 6, and 4 on horizontal gird, wherein 2 are located in XOZ planes, 2 are located in YOZ planes；2 in vertical beam
Individual, wherein 1 is located in XOY plane, 1 is located in YOZ planes.
6. wind-tunnel balance as claimed in claim 5, it is characterised in that：
Each measured zone sets 4 measuring points, that is, set 4 foil gauges and constitute a Wheatstone bridge, measures notched areas axle
To bending stress.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611023820.8A CN106768791B (en) | 2016-11-17 | 2016-11-17 | A kind of micro wind-tunnel balance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611023820.8A CN106768791B (en) | 2016-11-17 | 2016-11-17 | A kind of micro wind-tunnel balance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106768791A true CN106768791A (en) | 2017-05-31 |
| CN106768791B CN106768791B (en) | 2019-04-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201611023820.8A Active CN106768791B (en) | 2016-11-17 | 2016-11-17 | A kind of micro wind-tunnel balance |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108195554A (en) * | 2018-01-16 | 2018-06-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Six component optical fiber aerodynamics force measurement balances and output signal combined method |
| CN108414188A (en) * | 2018-03-22 | 2018-08-17 | 中国航空工业集团公司沈阳空气动力研究所 | It is a kind of to be used for and hang together the six component strain balance of double struts for playing CTS experiments |
| CN113670560A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN117906903A (en) * | 2024-03-18 | 2024-04-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Micro aerodynamic resistance measuring device and use method thereof |
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| US3447369A (en) * | 1967-10-27 | 1969-06-03 | Us Navy | Wind tunnel balance |
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| CN202182810U (en) * | 2010-06-03 | 2012-04-04 | 湖南大学 | Automobile wind tunnel force measurement balance supporting mechanism |
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| US3447369A (en) * | 1967-10-27 | 1969-06-03 | Us Navy | Wind tunnel balance |
| CN2235615Y (en) * | 1995-06-02 | 1996-09-18 | 中国航天工业总公司第七○一研究所 | Internal six-component strain balance |
| CN202182810U (en) * | 2010-06-03 | 2012-04-04 | 湖南大学 | Automobile wind tunnel force measurement balance supporting mechanism |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108195554A (en) * | 2018-01-16 | 2018-06-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Six component optical fiber aerodynamics force measurement balances and output signal combined method |
| CN108195554B (en) * | 2018-01-16 | 2023-08-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Six-component optical fiber aerodynamic force measurement balance and output signal combination method |
| CN108414188A (en) * | 2018-03-22 | 2018-08-17 | 中国航空工业集团公司沈阳空气动力研究所 | It is a kind of to be used for and hang together the six component strain balance of double struts for playing CTS experiments |
| CN113670560A (en) * | 2021-10-21 | 2021-11-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN113670560B (en) * | 2021-10-21 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Pneumatic load measuring device of horizontal tail |
| CN117906903A (en) * | 2024-03-18 | 2024-04-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Micro aerodynamic resistance measuring device and use method thereof |
| CN117906903B (en) * | 2024-03-18 | 2024-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Micro aerodynamic resistance measuring device and use method thereof |
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| Publication number | Publication date |
|---|---|
| CN106768791B (en) | 2019-04-16 |
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